Accession Number : ADA299194

Title :   A Flexible Plate Nozzle Design for an Operating Mach Number Range of 1.4 to 2.0.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Emmert, Terence G.

PDF Url : ADA299194

Report Date : MAR 1995

Pagination or Media Count : 175

Abstract : The design for a supersonic flexible plate nozzle is presented. The nozzle was required for a supersonic blow-down cascade wind tunnel facility at the Naval Postgraduate School's Gas Dynamics Laboratory. Overall dimensions were based on calculations of the required test section height and width which would give acceptable (2 minute) mn times over an operating Mach number range from 1.4 to 2.0. A two-dimensional, constant-plate thickness, multiple-jack screw configuration was the concept used to effect the nozzle geometry changes. Mention is made of a multi-disciplinary design optimization routine which helped to mle out a single-jack, variable-plate thickness configuration. The aerodynamic and structural analysis used in the design process is presented in detail. Preliminary drawings of the nozzle mechanism are included. (AN)

Descriptors :   *SUPERSONIC NOZZLES, *SUPERSONIC WIND TUNNELS, AERODYNAMIC CONFIGURATIONS, MATHEMATICAL MODELS, OPTIMIZATION, TWO DIMENSIONAL, FINITE ELEMENT ANALYSIS, STRUCTURAL ANALYSIS, AIR FLOW, THESES, BOUNDARY LAYER, COMPUTATIONAL FLUID DYNAMICS, FLOW FIELDS, AERODYNAMIC LOADING, GEOMETRY, MACH NUMBER, SUPERSONIC FLOW, DESIGN CRITERIA, HEIGHT, PRESSURE DISTRIBUTION, ASPECT RATIO, NOZZLE THROATS, NOZZLE GAS FLOW, STAGNATION PRESSURE, FLEXIBLE STRUCTURES, GAS COMPRESSORS, BLOWDOWN, CASCADES(FLUID DYNAMICS).

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE